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EP0234988B1 - Brennkammer für einen Treibsatz und deren Aufbau - Google Patents

Brennkammer für einen Treibsatz und deren Aufbau Download PDF

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Publication number
EP0234988B1
EP0234988B1 EP87400139A EP87400139A EP0234988B1 EP 0234988 B1 EP0234988 B1 EP 0234988B1 EP 87400139 A EP87400139 A EP 87400139A EP 87400139 A EP87400139 A EP 87400139A EP 0234988 B1 EP0234988 B1 EP 0234988B1
Authority
EP
European Patent Office
Prior art keywords
ring
conical
shell
dome
combustion chamber
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP87400139A
Other languages
English (en)
French (fr)
Other versions
EP0234988A1 (de
Inventor
Dino Crapiz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Societe Europeenne de Propulsion SEP SA
Original Assignee
Societe Europeenne de Propulsion SEP SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Societe Europeenne de Propulsion SEP SA filed Critical Societe Europeenne de Propulsion SEP SA
Publication of EP0234988A1 publication Critical patent/EP0234988A1/de
Application granted granted Critical
Publication of EP0234988B1 publication Critical patent/EP0234988B1/de
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
    • F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • F02K9/343—Joints, connections, seals therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S60/00—Power plants
    • Y10S60/909—Reaction motor or component composed of specific material

Definitions

  • the present invention relates to a rocket engine combustion chamber of the type comprising two bottoms, possibly partially perforated, and connected together by a cylindrical shell.
  • each of the bottoms and the intermediate shell from a filamentary composite material, for example of the carbon / epoxy resin type, the winding of the cylindrical shell can be carried out separately from that of the bottoms.
  • the ferrule is produced on previously wound funds or on a block of powder equipped with the funds and serving as a mandrel.
  • An object of the present invention is to eliminate these drawbacks while retaining the advantages of the prior art.
  • each bottom comprises a weakly conical skirt, the outer face of which is secured over at least part of its length to the inner face of the shell by means of a cylindrical connecting ring.
  • slotted conical having a cylindrical outer face and, at least opposite the conical skirt of the bottom, a conical face of the same conicity as said conical skirt, the assembly of the three elements to be joined, that is to say the bottom, ferrule and ring, being produced by bonding.
  • the various constituent elements can be subjected to heat treatments without it being necessary to take account of the reactive behavior of the content of the combustion chamber. Furthermore, the design according to the invention makes it possible to significantly reduce the extent of the anchoring or fixing areas of the bottoms on the shell and, consequently, to increase the volume available for filling with powder.
  • the invention also relates to a method for assembling the combustion chamber of a rocket engine comprising a cylindrical shell and added ends, all made by winding a filamentary composite material with a matrix of resin type.
  • this process is characterized in that the ferrule is first produced separately, the bottoms having two conical skirts and two cylindro-conical connecting rings, and the resin of these elements is polymerized before their assembly, the inner part of the shell receiving a bottom is coated with an adhesive, the outer face of the tapered skirt of the bottom and / or the tapered face and the cylindrical face of the cylindrical-conical ring, the bottom is placed at the desired location of the ferrule and, while holding it in place, the cylindrical-conical ring is introduced into the space between the ferrule and the conical skirt of the bottom until the ring comes to bear against the background and the adhesive is polymerized.
  • the combustion chamber 1 of a rocket engine comprises a cylindrical shell 2, at least two bottoms 3, 4 and a connecting ring 5, 6 for each of the bottoms 3, 4.
  • the cylindrical shell 2 and the added ends 3, 4 are produced separately from a wound filamentary composite material which may for example be of the carbon / epoxy resin type and are hot-polymerized at temperatures which may be higher than the self-temperature. inflammation of the powder.
  • the maximum outside diameter of the bottom 3, 4, that is to say the outside diameter of the large base of the conical skirt 3b, 4b, is slightly less than or at most equal to the inside diameter of the cylindrical shell 2.
  • the bottom for example 4, can, if necessary, consist of two different parts and have a skirt 4b connected to a base 4a comprising one or more openings 4c.
  • the connecting ring 5, 6 is of cylindro-conical shape and has at least one separation slot 7. When a single slot 7 is provided, it is advantageous that it extends over the entire length of the ring 5 , 6.
  • the external periphery 5a, 6a of the split ring 5, 6, intended to come into contact with the internal face of the ferrule 2 is cylindrical in shape over the entire length of the ring, while the internal periphery of the ring 5, 6 ′ comprises at least one conical part 5b, 6b which widens in the direction of the internal end of the ring.
  • the connecting ring 5, 6 may have, on its internal face, a cylindrical part 5 c, 6 c which is connected to the conical part 5 b, 6 b.
  • the length of the conical part of the ring 5, 6 is generally between 0.5 and 1.5 times the diameter of said ring.
  • the connecting ring 5, 6 is produced by winding in a filamentary composite material, for example of the glass / epoxy resin type, the polymerization of the resin being carried out hot at a temperature which may be higher than the auto-ignition temperature. powder.
  • the cylindrical-conical connecting ring 5, 6 may comprise several slots 8 in place of or in addition to the single separation slot 7.
  • the slots 8 are preferably distributed uniformly around the entire periphery of the ring 5, 6, start from the thinnest end thereof and cross, parallel to the axis of the ring 5,6, at least the entire conical part 5b, 6b thereof.
  • the external perimeter of the split ring 5, 6, when the edges of the slots 7 or 8 are in mutual contact with each other is 0.2 to 5 mm less than the internal perimeter of the cylindrical shell 2.
  • the powder can be introduced into the combustion chamber either after the establishment of a first base, for example 3, and before that of the second base 4, or after the establishment of the two funds 3, 4, provided that one of them, for example 4, is openwork.
  • the glue was polymerized hot. Two hydraulic burst tests were carried out at 344 and 346 bars respectively, without damaging the bottom-ferrule-ring connection, until failure at the connection bun with the base.
  • the length of the ring 5, 6 was 170 mm and, in the second case, 150 mm, while the bottom anchoring length (part of the bottom in contact with the ferrule and / or the ring) in the ferrule was 200 and 110 mm respectively. This shows that it is possible to reduce the length of the anchoring zones in a non-negligible way and at the same time increase the filling rate of the combustion chamber.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)
  • Toys (AREA)

Claims (6)

1. Brennkammer für einen Treibsatz vom Typ mit zwei Böden (3,4), die miteinander durch einen zylindrischen Ring oder Mantel (2) verbunden sind, wobei jeder Boden (3, 4) und der Zwischenring (2) aus einem Filament-Verbundwerkstoff gebildet sind, dadurch gekennzeichnet, dass jeder Boden (3,4) eine leicht konische Schürze (3b, 4b) aufweist, deren Aussenseite wenigstens auf einem Bereich ihrer Länge mit der Innenseite des Rings (2) mittels eines zylindro-konischen geschlitzten Verbindungsringes (5) verbunden ist, der eine zylindrische Aussenseite (5a und 6a) und wenigstens gegenüber der konischen Schürze (3b, 4b) des Bodens (3, 4) eine konische Innenseite (5b, 6b) von gleicher Konizität wie die konische Schürze (3b, 4b) aufweist, wobei die Anordnung der drei zu verbindenden Elemente, das heisst, des Bodens (3, 4), des Mantels (2) und des Rings (5, 6), durch Kleben verwirklicht ist.
2. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Konizität der konischen Schürze (3b, 4b) und jene des Verbindungsrings (5, 6) zwischen 0,2° und 5° (halber Kegelwinkel) beträgt.
3. Brennkammer nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass der Verbindungsring (5, 6) wenigstens einen Trennschlitz (7) aufweist, der sich über die gesamte Länge des Ringes erstreckt.
4. Brennkammer nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der Verbindungsring mehrere Schlitze (8) aufweist, die vom schlanksten Ende des Rings ausgehen und parallel zur Achse des Ringes wenigstens dessen gesamten Bereich der konischen Innenseite (5b, 6b) durchqueren.
5. Brennkammer nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass der Aussenumfang des geschlitzten Rings (5, 6), während die Schlitzränder (7, 8) in gegenseitigem Kontakt untereinander sind, geringer ist als 0,2 bis 5 mm bezüglich des Innenumfangs des zylindrischen Mantels (2).
6. Verfahren zum Zusammenbau einer Brennkammer für einen Treibsatz (1 ), die einen zylindrischen Mantel (2) und zusammengeführte Böden (3, 4) aufweist, welche alle aus einem Verbundwerkstoff mit Harzmatrix gebildet sind, dadurch gekennzeichnet, dass zunächst der Mantel (2), die zwei konische Schürzen (3b, 4b) aufweisenden Böden (3, 4) und zwei zylindro-konische Verbindungsringe (5, 6) getrennt hergestellt werden, und das Harz dieser Elemente vor ihrem Zusammenführen polymerisiert wird, der innere Bereich des Mantels (2), der einen Boden (3, 4) aufnimmt, mit einem Klebstoff überzogen wird, die Aussenseite der konischen Schürze (3b, 4b) des Bodens und/oderdie konische Innenseite (5b, 6b) und die zylindrische Aussenseite (5a, 6a) des zylindro-konischen Rings (5, 6) mit einem Klebstoff überzogen wird, der Boden (3,4) an den gewünschten Ort des Mantels (2) plaziert wird, und, während er an seinem Platz gehalten wird, der zylindro-konische Ring (5,6) in den Raum zwischen dem Mantel (2) und der konischen Schürze (3b, 4b) des Bodens eingeführt wird, bis der Ring (5, 6) in Anschlag gegen den Boden kommt, und dass die Polymerisation des Klebstoffs fortgesetzt wird.
EP87400139A 1986-01-22 1987-01-21 Brennkammer für einen Treibsatz und deren Aufbau Expired EP0234988B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8600877A FR2593238B1 (fr) 1986-01-22 1986-01-22 Chambre de combustion de propulseur et son procede d'assemblage
FR8600877 1986-01-22

Publications (2)

Publication Number Publication Date
EP0234988A1 EP0234988A1 (de) 1987-09-02
EP0234988B1 true EP0234988B1 (de) 1989-04-12

Family

ID=9331379

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87400139A Expired EP0234988B1 (de) 1986-01-22 1987-01-21 Brennkammer für einen Treibsatz und deren Aufbau

Country Status (6)

Country Link
US (1) US4787202A (de)
EP (1) EP0234988B1 (de)
JP (1) JPH0788806B2 (de)
DE (1) DE3760101D1 (de)
FR (1) FR2593238B1 (de)
NO (1) NO167597C (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2606082B1 (fr) * 1986-11-05 1991-04-05 Europ Propulsion Chambre de combustion de propulseur a propergol solide, et procede pour sa fabrication
US4911795A (en) * 1987-08-14 1990-03-27 Morton Thiokol, Inc. Method of preserving a composite material cased solid propellant rocket motor
US6281562B1 (en) 1995-07-27 2001-08-28 Matsushita Electric Industrial Co., Ltd. Semiconductor device which reduces the minimum distance requirements between active areas
AU8755398A (en) * 1997-02-28 1998-11-11 Russell A. Crook Case assembly including adhesive bond that is insensitive to high operating pressures and exhibits inherent high temperature relief capability, and mot or assembly and rocket assembly including the same
US7966809B2 (en) * 2006-02-01 2011-06-28 Spacedev, Inc. Single-piece hybrid rocket motor

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3173249A (en) * 1959-08-10 1965-03-16 Thiokol Chemical Corp Air-breathing solid propellant ducted rocket
DE1209364B (de) * 1962-12-06 1966-01-20 Thiokol Chemical Corp Feststofftreibsatz
US3243956A (en) * 1963-07-15 1966-04-05 Atlantic Res Corp Flexible support
US3296802A (en) * 1964-02-03 1967-01-10 Thiokol Chemical Corp Laminated material and arrangement thereof for use in pressure vessels
GB1203230A (en) * 1966-12-01 1970-08-26 Imp Metal Ind Kynoch Ltd Improvements in pressure vessels
FR2045201A5 (en) * 1969-06-19 1971-02-26 Ramont Jacques Expanding segment sealing device for chamb- - er under pressure
US3812671A (en) * 1971-08-26 1974-05-28 Textron Inc Rocket fuel supply system
FR2230490A1 (en) * 1973-05-25 1974-12-20 Hercules Inc Filament wound vessel - having inner and outer loosely fitting shells
FR2340490A1 (fr) * 1976-02-04 1977-09-02 Legoy Auguste Dispositif d'etancheite pour machine rotative a fluide hydraulique

Also Published As

Publication number Publication date
DE3760101D1 (en) 1989-05-18
NO870263D0 (no) 1987-01-21
JPH0788806B2 (ja) 1995-09-27
JPS62173235A (ja) 1987-07-30
NO167597B (no) 1991-08-12
FR2593238A1 (fr) 1987-07-24
NO167597C (no) 1991-11-20
US4787202A (en) 1988-11-29
NO870263L (no) 1987-07-23
EP0234988A1 (de) 1987-09-02
FR2593238B1 (fr) 1990-11-02

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